Modelling of non-uniform DC driven glow discharge in argon gas

Rafatov, İsmail; Akbar, Demiral; Bilikmen, Sinan

doi:10.1016/j.physleta.2007.02.073

Cited by 23 publications

(13 citation statements)

References 16 publications

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“…1 shows the thrust comparison with diffHUHQW ÀXLG PRG els and with the experimental data when applied voltage is 10 kV and d = 1 cm. It is apparent form 13) It should be noted that if electron secondary emission coefficient increases, the thrust also increases. The thrust and the current apparently vary with the secondary electron emission coefficient, which depends on the material of the electrode, the gas species and the operation condition.…”

Section: Thrust Evaluationmentioning

confidence: 98%

A Effect of Plasma Fluid Models on Prediction Accuracy of Electro-Hydrodynamic Thruster Performance

Shibata

Watanabe

Suzuki

2016

AEROSPACE TECHNOLOGY JAPAN

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Section: Thrust Evaluationmentioning

confidence: 98%

A Effect of Plasma Fluid Models on Prediction Accuracy of Electro-Hydrodynamic Thruster Performance

Shibata

Watanabe

Suzuki

2016

AEROSPACE TECHNOLOGY JAPAN

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“…The electron transport coefficients (µ e and D e ) are calculated using an electron Boltzmann equation solver, Bolsig+ [16], as functions of the mean electron energy (ε) and the energy transport coefficients are related to the particle transport coefficients via µ ε = (5/3 ) µ e and D ε = (5/3 ) D e . The ion mobility and diffusion coefficients are obtained from equation (17) in Rafatov et al [20], and Einstein relation,…”

Section: Ionized Gas Module (Igm)mentioning

confidence: 99%

Rarefied gas electro jet (RGEJ) micro-thruster for space propulsion

Blanco¹,

Roy²

2017

J. Phys. D: Appl. Phys.

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This article numerically investigates a micro-thruster for small satellites which utilizes plasma actuators to heat and accelerate the flow in a micro-channel with rarefied gas in the slip flow regime. The inlet plenum condition is considered at 1 Torr with flow discharging to near vacuum conditions (<0.05 Torr). The Knudsen numbers at the inlet and exit planes are ~0.01 and ~0.1, respectively. Although several studies have been performed in micro-hallow cathode discharges at constant pressure, to our knowledge, an integrated study of the glow discharge physics and resulting fluid flow of a plasma thruster under these low pressure and low Knudsen number conditions is yet to be reported. Numerical simulations of the charge distribution due to gas ionization processes and the resulting rarefied gas flow are performed using an in-house code. The mass flow rate, thrust, specific impulse, power consumption and the thrust effectiveness of the thruster are predicted based on these results. The ionized gas is modelled using local mean energy approximation. An electrically induced body force and a thermal heating source are calculated based on the space separated charge distribution and the ion Joule heating, respectively. The rarefied gas flow with these electric force and heating source is modelled using density-based compressible flow equations with slip flow boundary conditions. The results show that a significant improvement of specific impulse can be achieved over highly optimized cold gas thrusters using the same propellant.

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“…The interelectrode distance and radius of gas tube are d = 1 cm and R = 1.1 cm respectively. The values for mobilities and diffusion coefficients for electrons and Ar + ions are taken from (Rafatov et al, 2007;Fiala et al, 1994). The first Townsend ionization coefficient is obtained by fitting the experimental data (Stankov et al, 2015;Kruithof, 1940…”

Section: Fig 1 Discretization Of Inter-electrode Space In Two Dimensmentioning

confidence: 99%

“…In this paper, the continuity equation for particles was applied in the form in which it is used today. Following these papers, fluid models have been used very often for the modeling of different types of gas discharges (Lymberopoulos and Economou, 1993;Passchier and Goedheer, 1993;Rafatov et al, 2007;Golubovskii et al, 2003;Rafatov et al, 2012).…”

Section: Introductionmentioning

confidence: 99%

Two-dimensional fluid modeling of DC glow discharge in argon at low pressure

Stankov

Jovanović

Marković

et al. 2015

Facta Univ Phys Chem Technol

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The modeling of DC glow discharge in argon at the pressure p = 1.5 Torr and inter-electrode distance d = 1 cm was performed for different voltages and glow currents. For the first time, argon glow discharge is modeled using a two-dimensional (2D) fluid model with non-local ionization. A detailed numerical procedure for 2D fluid modeling is given. The 2D profiles of particle number densities and electric potential obtained from the fluid model with non-local ionization and the simple fluid model are presented and compared.

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Modelling of non-uniform DC driven glow discharge in argon gas

Cited by 23 publications

References 16 publications

A Effect of Plasma Fluid Models on Prediction Accuracy of Electro-Hydrodynamic Thruster Performance

A Effect of Plasma Fluid Models on Prediction Accuracy of Electro-Hydrodynamic Thruster Performance

Rarefied gas electro jet (RGEJ) micro-thruster for space propulsion

Two-dimensional fluid modeling of DC glow discharge in argon at low pressure

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